Propulsion assembly for aircraft

Abstract

The invention relates to a propulsion assembly for an aircraft, that comprises: a turbojet engine ( 1 ) including a fan casing ( 3 ) and an engine casing ( 5 ); a pylon for holding said turbojet engine ( 1 ); and a device for suspending said turbojet engine under the pylon, that comprises two front suspension connecting rods ( 9 ), two rear suspension connecting rods ( 11 ), and a thrust acceleration connecting rod ( 15 ) extending between the front portion ( 17 ) of said engine casing ( 5 ) and the pylon in a plane containing the axis (A) of said turbojet engine ( 1 ). An additional connecting rod ( 19 ) extends between said fan casing ( 3 ) and said pylon in a direction substantially parallel to that of the axis (A) of said turbojet engine.

The invention claimed is: 
     
       1. A propulsion assembly for an aircraft, comprising:
 a turbojet engine comprising a fan casing and an engine casing; 
 a pylon for supporting the turbojet engine; and 
 a device for suspending the turbojet engine beneath the pylon comprising:
 front suspension connecting rods extending between said fan casing and said pylon in a plane substantially perpendicular to an axis of said turbojet engine, 
 rear suspension connecting rods extending between a rear portion of said engine casing and said pylon in a plane substantially perpendicular to the axis of said turbojet engine, said rear suspension connecting rods being substantially parallel with one another 
 a thrust-absorbing connecting rod extending between a front portion of said engine casing and said pylon in a plane comprising the axis of said turbojet engine, and 
 an additional connecting rod extending between said fan casing and said pylon in a direction substantially parallel to that of the axis of said turbojet engine. 
 
 
     
     
       2. The propulsion assembly as claimed in  claim 1 , wherein all said connecting rods are connected by swivel joints to their respective members. 
     
     
       3. The propulsion assembly as claimed in  claim 1 , wherein directions of said front suspension connecting rods are substantially radial relative to the axis of said turbojet engine. 
     
     
       4. The propulsion assembly as claimed in  claim 1 , wherein said front suspension connecting rods are placed in a manner that is substantially symmetrical relative to a substantially vertical plane containing the axis of said turbojet engine. 
     
     
       5. The propulsion assembly as claimed in  claim 1 , wherein a direction of one of said rear suspension connecting rods is substantially radial relative to the axis of said turbojet engine. 
     
     
       6. The propulsion assembly as claimed in  claim 1 , wherein a direction of said rear suspension connecting rods is inclined relative to the vertical. 
     
     
       7. The propulsion assembly as claimed in  claim 1 , wherein said thrust-absorbing connecting rod is inclined relative to the axis of said turbojet engine.